DE3606549A1 - Method and device for producing (generating) a movement and for energy conversion - Google Patents

Abstract

A method is provided for producing movement and for energy conversion, in the case of which method at least two wings (F) with a streamlined profile are guided on a closed revolving path, the wing profile being varied during the revolution of the wings (F). In the case of a revolving unit (so-called roller wings), wings (F) having a variable profile are arranged on arms (5) such that they can pivot, which arms can rotate about a central axis (1). One or more such revolving units can be used in a wind or water power station or as drive and/or control units for an aircraft or water craft. <IMAGE>

Description

The invention relates to a method for generating movement or energy conversion by means of wings guided in a closed orbit, on one in particular to carry out the method certain device that rotates about a central axis bare arms and hinged wings has, and on applications of the method and Device and objects based on it.

An aircraft is known (DE-OS 27 57 732), at that instead of fixed wings on each side a rotor is arranged in the fuselage. Every rotor has two arms attached to a motor shaft Wings on one inside the profile and relative axis parallel to its front edge can be pivoted to the arms. With an off the wings are free to a limited extent pivotally attached to the arms, taking stops may be present to limit the pivoting movement nen. In another version there is a cam  actuated device provided one as a trim tuner designated position of the wing in certain and to change cyclically in such a way that the Change in the passage through the upper and lower Points of their circulation are done quickly.

In an aircraft with such rotors the functions of generating lift and propulsion of the two blades of the rotor when rotating met separately. This results in difficulties and shortcomings. The proposed aviation stuff has not been put into practice nen.

The invention is intended to show a way that using at least two, closed on one orbit over a 360 ° orbit led wing advantageous opportunities for movement generation or opened for energy conversion. The Be handle the creation of a movement is not just that in the sense of moving an object, such as an egg aircraft, to understand, but should also Include movements related to the conversion of Ener gie without changing the location of the unit used serve. The invention therefore also seeks sheep development of advantageous devices and objects, that are suitable for these purposes. More with everyone the related problems with which he concerned, result from the respective explanation the solution shown.

A method in which at least two wings with Streamlined profile in a closed orbit are performed, characterized according to the invention by the fact that the flü gel profile is changed.  

This allows the resultant Force flowing under the influence of a Medium is exerted on the circumferential wing torque in the same sense every time testifies. This is an advantage of extraordinary Be interpretation, which also has versatile application options opened. According to the invention, this is for the air driving, shipping and for wind and water power systems into consideration.

The change in the wing profile during circulation can be provide in various ways, especially in Dependable dependency on the rotation angle, depending change in the angle of attack of another wing, especially one diametrically opposite ordered wing, or by a wing around flowing medium itself.

When converting flow energy into rotary kinetic energy can turn the wing to an outside Maintain the same position during the rotation ten, with the wing profiles by adjusting mechanisms and the angle of attack can be changed sensibly, so that there is a continuous circulation. Analogous the same applies to the conversion of rotary kinetic energy in flow energy.

The invention is further directed to a Vorrich each with a streamlined profile Wings spaced radially from a central axis on parallel, together in one revolution Arms or the like rotatable about the central axis. held and are each pivotable about a wing axis. A such device is characterized according to the inven dung in that the wings have a changeable profile exhibit.  

The execution can be made so that the wing profile inevitably during a circulation of the arms is changeable, or so that the wing one under the influence of a medium flowing around them have changeable profile.

It can be the case that a profile change automatically due to centrifugal force and change in the angle of attack Passage through a dead center.

The wings can gel out of at least two kig interconnected parts exist for Ver changing the wing profile relative to each other are pivotable. Show another version the wings each have at least one area which elastically deformable to change the wing profile is. Both options can also be used together combine.

To change the wing profile, an outer Ver pivot drive can be provided, each with little at least one wing part or wing area in connection manure stands. The adjustment movement is from the outside forth in the wing part or wing area in question initiated. In particular, transmission elements can do this te such as gears, toothed belt drives or the like. intended be. The term external swivel drive falls not only a motor drive, but also such a design in which the adjustment movement to change the wing profile from the rotation of the Arms with the circulation unit containing the wings is headed.

A swivel drive can also be between two There are two wing parts or wing areas  be. This is particularly advantageous in some cases.

Regardless of the arrangement, training, adjustability or profile change possibility of the wing a favorable embodiment of the device in that a frame part supporting the arms with the wings, Support body or the like at an angle around the central axis is adjustable, such that an outer loading traction point for changing the profile and angle of attack the wing according to the respective conditions can be chosen, especially with regard to the Adaptation to a flow direction. Very cheap is this in connection with a version in which also setting means for the angle of attack and / or the profile of the wings in their position relative to an external reference point are changeable, in particular by swiveling around the central axis.

The device according to the invention can be versatile use and apply. In particular, it can be part a wind or hydropower plant and continue to be as a drive and / or control unit for an air or watercraft.

An aircraft with a recirculating unit of the explanat Tert kind can start vertically, in Horizon move downhill and above all without driving the Recirculation unit assume a gliding condition.

Because of the versatile setting options it is the position of the central axis of the Device in the room according to the needs and Conditions to choose. You can in particular scales be arranged right or vertical.

The device or the circulation unit can be met fend referred to as "roller blades".  

Further details, features and advantages of the Erfin the following explanation of exemplary embodiments, from the associated drawing and from the claims. Show it:

Fig. 1 is a representation of de illustrate the principle of the invention, in one embodiment,

Fig. 2 shows another embodiment wings,

FIGS. 3 and 4 two embodiments of the device as a wind or water turbine, each in largely schematic representation;

Fig. 5 is a plan view of Fig. 4,

Fig. 6 shows an aircraft in a side view, largely schematic,

Fig. 7 is a front view of FIG. 6,

FIGS. 8 and 9, the aircraft of FIG. 6 each in other flight conditions,

FIGS. 10 and 11 in view and plan view Steuermög possibilities in vertical flight,

FIGS. 12 and 13, a ship propulsion system in side view and plan view,

Fig. 14 is an embodiment of a device with gear-change to the airfoil angle of attack and in side view,

15 shows a section along the line XV-XV in FIG. 14,

Fig. 16 is a vertical section of FIG. 14, the arms being drawn with the wings rotated relative to FIG. 14 through 90 °,

FIG. 17 parts of the transmission device in a section along the line XVII-XVII in Fig. 16,

Fig. 18 shows another embodiment of the device in one of the Fig. 16 similar representation,

Fig. 19 shows a device for changing the airfoil and

Fig. 20 is an actuator for changing the angle of attack.

In Fig. 1, an assembly equipped with four wings F is shown, which can rotate around a central axis. Each wing F consists of a middle part 2 , a front part 3 and a rear part 4 . The middle parts 2 of the wing F are mounted at the ends of paral lelen arms 5 , such that they can perform a Schwenkbe movement about a wing axis 6 . The front part 3 of each wing F and also the rear part 4 is in each case articulated verbun with the central part, such that the part 3 is pivotable relative to the central part 2 about a pivot axis 7 and the part 4 about a pivot axis 8 .

The arrows M denote a medium flowing in the direction R , for example air or water. With the letter a the angle of attack of the wing F is referred to with respect to the direction R of the flowing medium. It is indicated here with a center line through the wing axis 6 to the middle part 2 . However, it can also be designated by the dash-dotted profile chord A with reference to the flow direction R.

In the device shown in FIG. 1, not only the angle of attack a changes with one revolution of the wing F , but there is also a change in the profile of the wing F during the revolution. This happens so that a rotating movement of the arms 5 with the wings F takes place with a corresponding moment in the same direction of rotation by the inflowing medium.

As indicated above and below the wing F by arrows, a negative pressure arises over the convex curved side of the wing and an upper pressure on the opposite hollow profile side. This results in a force which causes the rotation of the assembly in accordance with the torque determined by the length of the arms 5 . At the top and bottom dead center, the profile of the wings F has an elongated neutral shape. The forces acting on both sides of the wing cancel each other out. In these dead centers, the angle of attack and the profile shape of the wing is turned, so that in the right wing in Fig. 1, the force L is not directed upwards as in the left wing, but downwards, so that the corresponding moment on both wings in same sense of rotation. Depending on the existing number of wings, the rotational movement through the respective dead center is continued by the moment acting on the other wings or by the moment of inertia.

For changing the angle of attack and the wing profile there are various options, what next un is still being considered.  

In the embodiment shown in Fig. 1, the wings F consist of a plurality of parts which are articulated to one another and which parts 2 , 3 , 4 can be pivoted relative to one another in order to change the wing profiles. Furthermore, it is possible to design the wings so that they each have at least one area which is elastically deformable to change the profile. In Fig.2 such a wing F 'is shown with its wing gel axis 6 , the rear half 9 can be brought from a neutral position in the dot-dash positions by appropriate deformation relative to the front wing part. This makes it possible to set the profile shape on each side in a convex and concave manner, just like a wing made of articulated parts. For this purpose, suitable actuatable actuating elements can be provided in the interior of the wing.

The device shown in FIG. 3 is a wind or hydropower plant, the inflowing medium in turn being marked with the letter M and the inflow direction being marked with the letter R. The circulation unit with two arms 5 and wings F pivotally mounted thereon about the wing axes 6 is arranged with a horizontal central axis 1 in a base body or frame G with parallel side arms 11 supporting the central axis 1 , the cheeks 11 with their base 12 connecting them so are mounted on a base 13 that the unit can be rotated about a vertical central axis V. This makes it possible to turn the wing unit in the main flow direction. The change in the angle of attack and the profile of the wing is done analogously, as was explained in connection with FIG. 1. When the flow rate changes, the speed of the circulation unit can be influenced by changing the profile and angle of attack, or even stopped (e.g. if the flow rate is too high) by pivoting the angle of attack and profile in a neutral manner ( Fig. 1 above and below).

From the circulation unit (roller wing) with the wings F is a machine or directly driven via a gear, such as a generator, a pump or the like. The design can also be made so that several circulation units with arms and wings are arranged side by side and then work, for example, on a generator.

In Figs. 4 and 5 an apparatus is shown in which the central axis 1 of the circulation unit with arms 5 and wings F is arranged vertically. The letter G denotes a corresponding frame or a base body. A connection, not shown, leads to a driven machine. Such a version with a vertical central axis is expedient in a wind turbine, inter alia, when the wind direction changes little or the wind comes mainly from two directions, for example sea wind and land wind. Adjustment means for the profile shape and the angle of attack of the blades are simply adjusted to the wind direction.

Designs as shown in FIGS. 3 to 5 or similar designs are also suitable for use as a hydropower plant. The flow energy of the water can act on a large area with a suitable wing arrangement and choice of suitable dimensions, so that even a slowly flowing current (rivers, streams, tides) makes a conversion into rotating energy possible. A circulation unit with wings can be arranged horizontally as well as vertically with its central axis.

A device of the type described or similar does not require the construction of a dam and is very quickly ready for use, especially with relative small design.

In Figs. 6 to 9 is the use of a circulating unit illustrated with wings for aircraft with a few examples. The previously known flight devices that are heavier than air, need wings to generate a buoyancy force and drives (propellers, nozzles or the like.) For generating a driving force before. The helicopter or rotary wing is an exception. Despite numerous possible uses, this has a number of significant disadvantages. These are not available in an aircraft with one or more circulation units (roller blades) of the type described.

In Figs. 6 to 9 of the body or hull is referred to an aircraft with the letter Z. The aircraft contains a cabin with a cockpit and a three-legged landing gear B, for example. A circulation unit U with a horizontal central axis is mounted in a structure or frame G. In the example shown, it has two arms 5 , which can also be designed as a disk, with wings F. However, more than two arms with wings can also be provided. The number 15 is a movable control fin on the aerospace tool Z for vertical flight and the number 16 denotes a rudder for horizontal flight.

Depending on the change in the angle of attack and the profile shape of the wing F , the direction R of the air flow generated when the recirculating unit rotates can be changed. The rotation of the circulation unit U is generated by a motor, not shown, in or on the aircraft Z via corresponding transmission members.

An equipped with a circulation unit according to the invention can take off vertically. The profile shape and the angle of attack of the wing F is set so that the air flow is directed downward. This is shown in Fig. 8. If the wing is swiveled slightly to the front by a different position of the wing, the aircraft flies backwards.

If, after a vertical take-off, the direction of the air flow is gradually swiveled backwards by changing the wing setting, the vertical flight changes to horizontal flight to the front. This state is illustrated Fig. 6.

Direction control of the aircraft Z can take place in the vertical flight and in other flight conditions by means of the control fin 15 . This can be tilted about a horizontal axis in two directions and advantageously also rotatable about a vertical axis, as illustrated in FIGS. 10 and 11 in principle.

Tilting the control fin 15 allows since the aircraft's union flight in the direction of the central axis 1 of the circulation unit, depending on the direction of tilt direction to the left or to the right.

If the control fin 15 is rotated, there is a control of the aircraft Z about the vertical axis, about which the aircraft then rotates.

In horizontal flight the wings take over the orbit aggregates both the buoyancy and the propulsion. By turning the arms with the wings and by the setting of the angle of attack displaces the wings  the air. The force generated by this ensures automatically for the right one, twice for each round changed profile shape. So it’s not necessary Means for an inevitable change in the profile shape to be provided depending on the rotation angle. It read However, such funds should be provided that are then un can be supportive.

The aircraft with a circulation unit U of the type explained can also move without gliding the last one in gliding flight. For this purpose, a positive angle of attack and a positive profile are generated on all blades. Such a flight condition is illustrated in FIG. 9. In the event of an engine failure, the aircraft can be flown and landed like a glider with the stationary recirculating unit. The circulation unit is expediently locked so that it is stationary.

Deviating from the embodiment shown in FIGS . 6 to 9, the circulation unit U can also have more than two blades, as is basically also the case for other applications.

Instead of a recirculating unit, an aviation there are also several such units, especially right and left one through the fuselage or a gondola going vertical longitudinal median plane.

A circulation unit of the type according to the invention is also suitable for driving and controlling a ship, as illustrated only by way of example in FIGS. 12 and 13. Here, a circulation unit U with a vertical central axis 1 is attached to the stern of a ship S. The ship can be controlled by adjusting the direction of the water flow generated and moved in the desired manner.

There can also be one circulation unit at the bow and one at the stern of the ship. With appropriate ver Position of the flow direction can be the ship turn on the spot or drive sideways.

Furthermore, one or more circulation units also with horizontal arrangement of the central axis be seen. In particular, this can be the case with a Submersible be the case where the changeable Flow direction for rapid descent or emergence lets use.

The drive of the circulation unit can be used in water driving as with the aircraft, by any suitable tool engine, such as an engine or other engine respectively.

14 to 17, an implementation of the device with gear elements for changing the angle of attack and the profile shape of the wing F is explained in a recirculating unit, again designated by the letter U , with reference to FIGS . 14 to 17.

In a frame or base body G , the circulation unit U is mounted in bearings 18 so that it can perform a rotation around the central axis 1 . The arms of the circulating unit are also designated by the number 5 here. In it, the wings Fa and Fb, which are formed in three parts in this example as well as in FIG. 1, are each pivotably supported with their central part 2 . A front part of each wing is denoted by the number 3 and a rear part by the number 4 , as in FIG. 1, the respective front part 3 relative to the central part 2 about the axis 7 and the rear part 4 relative to the central part 2 is pivotable about the axis 8 , thereby changing the profile shape. A pivoting about the wing axis 6 a or 6 b serves to change the angle of attack.

The rotary movement of the circulation unit about the central axis 1 is transmitted through sprockets 19 via chains to the outside on sprockets 10 and via a shaft 17 firmly connected thereto to a generator 14 , in which electrical energy is thus generated. In another application of the circulation unit U , a motor is provided instead of the generator, through which the circulation unit is then reversed.

Numbers 73 and 74 denote two levers, one of which is connected to a hollow shaft 43 and the other to a shaft 42 arranged concentrically therein and located in the central axis 1 . From the shafts 42 and 43 lead gear connections to the wings Fa and Fb . With a rotation of the rotating assembly U , the wings would not change their position and shape if there was no change on the levers 73 and 74 . If the lever 73 is pivoted to the left and the lever 74 to the right about the central axis 1 with reference to FIG. 14, then the wing axis 6 a is rotated by the same angle about the gear wheels 75 , 76 , 77 which are in engagement with one another the lever 73 was also pivoted. The chain of gears 78 , 79 and 80 rotates the wing axis 6 b by the same angle by which the lever 74 is pivoted. It follows from this that with such a movement of the levers 73 and 74 the angle of attack of the wings Fa and Fb is changed in opposite directions.

By means of further gear elements, it is possible to change the profile shape of the wing in a specific assignment to the setting angle. The gear 75 , which adjusts the vane axis 6 a , conducts a rotational movement further via gears 21 , 22 to a toothed segment 23 , which, via a further toothed element 24, the rear part 4 of the right in FIG. 14 and in FIG. 16 and 17 lower wing Fb about the pivot axis 8 rotates ent opposite. At the same time, the gear wheel 22 rotates in the same direction through a recess 26 by means of bearing bolts 27 fastened in the wheel 22 and by means of tabs 28 and bearing bolts 29, a plate 31 which is firmly connected to the front wing part.

The gear 78 , which rotates the wing axis 6 b , transmits the rotary motion further via a gear 32 to a gear 33 and thus via a toothed segment 34 to a toothed element or gear 36 connected to the rear part 4 of the wing Fa and rotates there by Wing part opposite. At the same time, the gear 33 rotates by means of bearing bolts 37 fastened therein via tabs 38 and bearing bolts 39, a plate 40 which is firmly connected to the front wing part 3 of the wing Fa , in the same direction.

The gear 78 sits on the shaft 42 and is thus firmly connected to the lever 74 . The hollow shaft 43 , in which the shaft 42 is rotatably mounted, rigidly connects the gear 75 to the lever 73 . The hollow shaft 43 is in turn mounted in a frame part 20 which also includes the arms 5 , as shown in FIG. 16. The frame part is rotatably supported in the frame G via the bearings 18 mentioned.

Two cams 45 and 46 perform at one revolution of the rotary unit U or the frame part 20 also one revolution each, as a result of the movement transmission from the frame part 20 via toothed wheels 47 and 48 . In the same ratio, a gear 49 with a firmly connected cam disc 50 and a gear 51 with a cam 52 firmly connected thereto are rotated. Each of the levers 73 and 74 at the end carries two followers 53 , for example roller bearings, which run on the circumference of the cams.

The cams 45 and 46 are designed such that the levers 73 and 74 are turned outwards with a half turn of the rotating assembly U or the frame part 20 with the arms 5 ( FIG. 14) and are turned inward during the second half turn . The transition curves from the large to the small radius of the cams describe the movements of levers 73 and 74 . During this movement, the change in profile and angle of attack takes place in the area of the top and bottom dead center of an entire orbital movement of 360 °, for which purpose FIG. 1 is also to be compared. The two cams 50 and 52 ensure that levers 73 and 74 are positively guided.

A bracket or bearings of the wheels 48 , 49 and 51 bil dender part 44 is pivotable about the central axis 1 . This pivoting movement can be effected via a rotatable worm 55 and a helical spur gear 54 which engages in it. The worm 55 can be rotated by hand or by means of a servo motor. The pivoting movement could also be done via a rack or lever.

If the position of the gear 48 with respect to the Zen tralachse 1 changed by a pivoting movement, who also the levers 73 and 74 and the cam discs abge them keyed ver pivots about the central axis 1 . With such a swivel adjustment, the points of the profile change are adjusted in the circumferential direction of the device. By such an adjustment of the profile change points, the Vorrich device can be optimally adjusted to any flow direction of a medium transversely to the central axis 1 . If it is not a question of generating movement by means of a medium acting on the circulating unit U , but rather driving the circulating unit by means of a motor for generating a movement of the device, the flow direction of the medium in question can be adjusted by the described adjustment of the profile change point (eg air) can be determined.

In the embodiment according to FIG. 18, corresponding or similar parts as in the embodiment according to FIGS . 14 to 17 are designated with the same reference numbers. There is a driven by the gear 48 rotary encoder 58 is provided, from which the levers 73 and 74 with the help of individual drives 62 (hydraulic or electromagnetic devices) can be moved controlled ( Fig. 20). Thereby, the angle of attack of the wings F via gear wheels, chain or toothed belt drives 61 or the like can be changed in a further manner.

While are present in the embodiment of the device according to FIGS. 14 to 17 outer adjustment means for changing the wing profile, Fig. 19 shows a oth er embodiment, wherein the individual drives 59 for Verschwen ken of a wing portion 3 and 4 relative to a ande ren wing part , here a middle wing part 2 , are seen before. The middle wing part 2 has egg NEN attachment point or an abutment 63 for such individual drives 59 . These are shown here as pressure-actuated cylinder-piston units, but can also be of a different type and design, such as electromechanical units. The energy supply of such individual drives 59 , which, contrary to the schematic illustration in FIG. 19, is expediently accommodated in the wings themselves, can take place via rotary unions 60 on the respective axes, as is illustrated in FIG. 18.

If the circulation unit is driven by a motor and then displaces a medium by adjusting the angle of attack a accordingly, the drive or actuating elements 59 for profile adjustment shown in FIG. 19 could also be dispensed with, because then the displacement counterforce for the correct profile shape worries.

When used as an aircraft, however, such adjusting elements 59 are advantageous, because in this way the profile can be pivoted against the air force when the rotating assembly is not rotating (cf. FIG. 9) and thus a gliding flight is possible, for example for landing.

With circulation units driven by flow energy gaten (so wind or hydropower machines) is the Profile shape advantageously inevitable by appropriate Drive elements in various designs set or change before described type, because here the flow force counteracts the profile.

All mentioned in the above description or Features shown in the drawing are intended, if the known state of the art allows for itself alone or in combinations as under the inven be considered falling.

Claims (27)

1. A method for generating a movement by means of at least two, each having a streamline profile, on a closed orbit over a Umlaufwin angle of 360 ° guided wings, in particular with change tion of the angle of attack of the wing during circulation, characterized in that during the rotation of the wing the wing profile is changed. 2. The method according to claim 1, characterized in that a change in the wing profile in a predefinable dependency speed of the rotation angle is made. 3. The method according to any one of claims 1 and 2, characterized characterized in that a change in the profile of a Wing depending on a change in employment angle of another wing is made.   4. The method according to claim 1, characterized in that the wing profile by a flowing around the wing Medium is changed. 5.Device with a streamline profile each having wings which hold a radial distance from a central axis on parallel arms or the like which can be rotated together in a circular movement about the central axis and the like and which can each be pivoted about a wing axis, in particular with a device, by means of which the angle of attack of the wing can be influenced in a predeterminable manner when the arms rotate, in particular for carrying out the method according to one of claims 1 to 4, characterized in that the wing gel ( F , F ') have a changeable profile. 6. The device according to claim 5, characterized in that the wing profile is inevitable during a Umlau fes of the arms ( 5 ). 7. The device according to claim 5, characterized in that the wings ( F , F ') a variable under the action of a medium flowing around them aufwei sen. 8. Device according to one of claims 5 to 7, characterized in that the wings ( F ) each consist of at least two articulated parts ( 2 , 3 , 4 ) which are pivotable relative to each other for changing the wing profile. 9. Device according to one of claims 5 to 7, characterized in that the wings ( F ') each have at least one area ( 9 ) which is elastically deformable for changing the wing profile. 10. Device according to one of claims 5 to 9, characterized in that in each case at least one wing part ( 3 or 4 ) or wing area with an external Ver pivot drive is in communication. 11. Device according to one of claims 5 to 10, that for the change of wing profile and angle of attack levers ( 73 , 74 ) are provided as adjusting elements, which contain the arms ( 5 ) and the wings ( F ) containing circulation unit with every half revolution ( U ) the profile and angle of attack change via gear links such as toothed wheels, toothed belts, chain drives or the like. cause. 12. The apparatus according to claim 11, that the levers cam discs ( 45 , 46 ; 50 , 52 ) are assigned. 13. Device according to one of claims 5 to 12, characterized in that at least one pivoting drive ( 59 ) between two wing parts ( 3 , 2 or 4 , 2 ) or wing areas is provided. 14. Device according to one of claims 5 to 13, characterized in that pressure-actuated devices ( 59 , 60 , 62 ) are provided as adjusting members for the wing profile and / or the angle of attack, which are controllable by sensors. 15. The device according to one of claims 5 to 13, characterized characterized in that as, adjusting elements for the wing profile and / or the angle of attack electric single drive be provided that are controllable by donors. 16. The device according to one of claims 5 to 15, characterized in that the arms ( 5 ) supporting frame part, support body ( 44 ) or the like. At an angle around the central axis ( 1 ) is adjustable, such that thereby external reference point for the profile and angle of attack change of the wing ( F ) a flow direction is adaptable bar. 17. The device according to one of claims 5 to 16, characterized characterized by their use as part of a water power plant. 18. Device according to one of claims 1 to 16, characterized is characterized by its use as part of a wind power investment. 19. Device according to one of claims 17 and 18, characterized in that several circulation units ( U ) on egg ne machine, a generator ( 14 ) or the like. are connected. 20. Device according to one of claims 5 to 16, characterized by its use as a drive and / or control unit for an aircraft ( Z ). 21. The apparatus according to claim 20, characterized in that above a gondola, a missile or the like. at least one circulation unit ( U ) which can be driven by one or more motors is provided. 22. The apparatus according to claim 21, characterized in that below the circulation unit ( U ) at least one tiltable and / or rotatable control fin ( 15 ) is vorgese hen. 23. The device according to one of claims 20 to 22, characterized in that the profile and / or the angle of attack of the wing ( F ) is adjustable so that the air force ( L ) is directed upwards when the circulation unit ( U ) is at a standstill, corresponding to a gliding condition. 24. Device according to one of claims 20 to 23, characterized in that the aircraft ( Z ) is provided with normal rudder devices. 25. Device according to one of claims 5 to 16, characterized by its use as a drive and / or control unit for a watercraft ( S ). 26. Device according to one of claims 5 to 25, characterized in that the central axis ( 1 ) is arranged horizontally. 27. The device according to one of claims 5 to 25, characterized characterized in that the central axis is perpendicular is arranged.